US7372556B2 - Apparatus and methods for inspecting a composite structure for inconsistencies - Google Patents

Apparatus and methods for inspecting a composite structure for inconsistencies Download PDF

Info

Publication number
US7372556B2
US7372556B2 US11/264,076 US26407605A US7372556B2 US 7372556 B2 US7372556 B2 US 7372556B2 US 26407605 A US26407605 A US 26407605A US 7372556 B2 US7372556 B2 US 7372556B2
Authority
US
United States
Prior art keywords
section
frame
light
laser
mirror
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active, expires
Application number
US11/264,076
Other versions
US20070097359A1 (en
Inventor
Roger W Engelbart
Reed Hannebaum
Tim Pollock
Sam Orr
Jeff Putnam
Eric Rector
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Boeing Co
Original Assignee
Boeing Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Boeing Co filed Critical Boeing Co
Priority to US11/264,076 priority Critical patent/US7372556B2/en
Assigned to BOEING COMPANY, THE reassignment BOEING COMPANY, THE ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: ENGELBART, ROGER W., POLLOCK, TIM, RECTOR, ERIC, HANNEBAUM, REED, ORR, SAM, PUTNAM, JEFF
Priority to JP2008538119A priority patent/JP5410092B2/en
Priority to KR1020087002537A priority patent/KR100996335B1/en
Priority to ES06849022T priority patent/ES2734901T3/en
Priority to AU2006333500A priority patent/AU2006333500B2/en
Priority to CA2615117A priority patent/CA2615117C/en
Priority to PCT/US2006/042717 priority patent/WO2007078408A2/en
Priority to EP06849022.6A priority patent/EP1943502B1/en
Publication of US20070097359A1 publication Critical patent/US20070097359A1/en
Publication of US7372556B2 publication Critical patent/US7372556B2/en
Application granted granted Critical
Active legal-status Critical Current
Adjusted expiration legal-status Critical

Links

Images

Classifications

    • GPHYSICS
    • G01MEASURING; TESTING
    • G01NINVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N21/00Investigating or analysing materials by the use of optical means, i.e. using sub-millimetre waves, infrared, visible or ultraviolet light
    • G01N21/84Systems specially adapted for particular applications
    • G01N21/88Investigating the presence of flaws or contamination
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B29WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29CSHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28Shaping operations therefor
    • B29C70/30Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/38Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
    • B29C70/386Automated tape laying [ATL]
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B29WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29CSHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28Shaping operations therefor
    • B29C70/30Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/38Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
    • B29C70/382Automated fiber placement [AFP]
    • GPHYSICS
    • G01MEASURING; TESTING
    • G01NINVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N21/00Investigating or analysing materials by the use of optical means, i.e. using sub-millimetre waves, infrared, visible or ultraviolet light
    • G01N21/84Systems specially adapted for particular applications
    • G01N2021/8472Investigation of composite materials
    • GPHYSICS
    • G01MEASURING; TESTING
    • G01NINVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N21/00Investigating or analysing materials by the use of optical means, i.e. using sub-millimetre waves, infrared, visible or ultraviolet light
    • G01N21/84Systems specially adapted for particular applications
    • G01N21/88Investigating the presence of flaws or contamination
    • G01N21/8851Scan or image signal processing specially adapted therefor, e.g. for scan signal adjustment, for detecting different kinds of defects, for compensating for structures, markings, edges
    • G01N2021/8854Grading and classifying of flaws
    • G01N2021/8867Grading and classifying of flaws using sequentially two or more inspection runs, e.g. coarse and fine, or detecting then analysing
    • GPHYSICS
    • G01MEASURING; TESTING
    • G01NINVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N2201/00Features of devices classified in G01N21/00
    • G01N2201/06Illumination; Optics
    • G01N2201/063Illuminating optical parts
    • G01N2201/0635Structured illumination, e.g. with grating
    • GPHYSICS
    • G01MEASURING; TESTING
    • G01NINVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N2201/00Features of devices classified in G01N21/00
    • G01N2201/06Illumination; Optics
    • G01N2201/063Illuminating optical parts
    • G01N2201/0636Reflectors

Definitions

  • the present disclosure relates generally to automated material placement machines and their use. More particularly (but not exclusively) the present disclosure relates to systems and methods for inspecting material laid by an automated material placement machine.
  • the present disclosure in one aspect, is directed to a method of inspecting material laid by a material placement machine.
  • Light is directed onto the material in a direction essentially normal to the material to illuminate a section of the material.
  • Laser energy is projected onto the section at an angle predetermined to reveal inconsistencies in the section.
  • the disclosure is directed to a system for inspecting material laid by a material placement machine.
  • the system includes a mirror and one or more light sources configured to project light onto the mirror.
  • the mirror is configured to reflect the projected light onto a section of the material in a direction essentially normal to the section.
  • One or more laser sources are configured to project laser energy onto the section at an angle predetermined to reveal inconsistencies in the section.
  • the disclosure is directed to a system for inspecting material laid by a material placement machine.
  • the system includes a mirror suspended over a section of the material that has been laid.
  • the mirror has one or more transparent portions.
  • One or more light sources are configured to project light onto one or more reflective portions of the mirror.
  • the mirror is further configured to reflect the projected light onto the material section in a direction essentially normal to the section.
  • One or more laser sources are configured to project laser energy onto the section at an angle predetermined to reveal inconsistencies in the section.
  • One or more cameras are configured to record the section through the one or more transparent portions of the mirror.
  • FIG. 1 is a block diagram of a material placement system in accordance with one implementation of the disclosure
  • FIG. 2 is a block diagram illustrating a method of inspecting material laid by a material placement system in accordance with one implementation of the disclosure
  • FIG. 3 is a side perspective view of a system for inspecting material laid by a material placement system in accordance with one implementation of the disclosure
  • FIG. 4 is a top/side perspective view of a system for inspecting material laid by a material placement system in accordance with one implementation of the disclosure
  • FIG. 5 is a bottom/side perspective view of a system for inspecting material laid by a material placement system in accordance with one implementation of the disclosure
  • FIG. 6 is a top view of a system for inspecting material laid by a material placement system in accordance with one implementation of the disclosure
  • FIG. 7 is a bottom view of a system for inspecting material laid by a material placement system in accordance with one implementation of the disclosure.
  • FIG. 8 is an illustration of a section of illuminated material and its image in a frame displayed on a user interface screen in accordance with one implementation of the disclosure.
  • the disclosure is directed to systems and methods of inspecting material laid by a material placement machine.
  • the placement machine could be, for example, a multi-head tape lamination machine (MHTLM), a fiber placement (FP) machine, or a contour tape lamination (CTL) machine.
  • MHTLM multi-head tape lamination machine
  • FP fiber placement
  • CTL contour tape lamination
  • a block diagram of an exemplary material placement system is indicated generally in FIG. 1 by reference number 20 .
  • a material placement machine 24 is used to lay down composite material 28 onto a substrate 32 to fabricate a composite structure.
  • the machine 24 includes a roller, compaction shoe and/or other component, numbered as 36 and dependent on the type of placement machine, for laying the material 28 onto the substrate 32 .
  • the system 20 includes a processor 40 having a memory and/or storage device 44 .
  • the processor 40 is in communication with the machine 24 .
  • a user interface 50 may be, e.g., a computer monitor including a display screen 54 and an input device such as a keyboard and mouse (not shown).
  • the user interface 50 is in communication with the processor 40 .
  • a width of the material 28 is newly laid on the substrate 32 by the machine 24 .
  • Light is directed onto the material 28 in a direction 120 essentially normal to the material to illuminate the material. Specifically and for example, the light is projected from a light source 124 onto a reflective surface 128 and reflected by the surface 128 onto the material 28 to illuminate a section 132 of the laid material.
  • the method 100 also includes projecting laser energy onto the section 132 at an angle predetermined to reveal inconsistencies in the section 132 .
  • a laser source 140 projects the laser energy as one or more lines 144 onto the section 132 . The lines or stripes are projected, for example, across an axis 148 of placement of the material 28 . It should be noted that other implementations are contemplated in which different laser patterns and/or laser projection orientations may be used.
  • the light source 124 above the material 28 may be configured to illuminate a full width of the material 28 .
  • the laser striping 144 can reveal gaps and/or overlaps in the material 28 . Additionally, the striping can enhance the illumination from the light source 124 and can help reveal such items as fuzz balls, resin balls, and backing materials.
  • the present method can be implemented in various ways on various placement machines. Additionally, and as further described below, implementations of the present method can be scaled to various widths of material to be inspected. For example, although a single light source 124 and a single laser source 140 are used in the implementation 100 , a plurality of light sources and/or a plurality of laser sources may be used in other implementations.
  • FIGS. 3-7 One exemplary embodiment of a system for inspecting material laid by a material placement machine is indicated generally in FIGS. 3-7 by reference number 200 .
  • the system 200 includes a frame 204 having brackets 208 configured for attachment to a placement machine, e.g., the machine 24 (shown in FIG. 1 ). It should be noted that other embodiments of the system 200 could be configured in various ways in relation to material placement machines, dependent on width of material to be inspected and placement machine configuration.
  • component 36 of the machine 24 is a compaction roller.
  • the frame 204 is configured for attachment, for example, above and behind the compaction roller 36 such that the frame 204 overhangs newly laid material 28 .
  • a mirror 212 is mounted in the frame 204 , for example, at a 45-degree angle. The mirror 212 is at least partially silvered to provide one or more reflective portions.
  • a plurality of light sources 216 are mounted, for example, such that they project light essentially parallel to an axis 220 of placement of the material 28 . Light from the light sources 216 may be projected toward the mirror 212 and reflected by the mirror reflective portion(s) onto the material 28 in a direction essentially normal to the material.
  • a plurality of laser sources 224 mounted to the frame 204 are configured to project laser energy directly onto the material 28 at an angle predetermined to reveal inconsistencies in the material.
  • the laser sources 224 may be, for example, LasarisTM SNF line lasers by StockerYale, Inc. of Salem, N.H.
  • a plurality of cameras 230 are mounted in the frame 204 above the mirror 212 .
  • the cameras 230 are configured to image, through one or more transparent portions 234 of the mirror 212 , a section of the material 28 illuminated by the light and laser sources 216 and 224 .
  • the cameras 230 may be actuated, for example, by the processor 40 , which receives images from the cameras 230 and/or memory 44 .
  • the processor 40 may process the images to facilitate reliable detection of inconsistencies.
  • the cameras 230 are, for example, Sony XC-HR50 cameras, although other cameras could be used.
  • the cameras 230 collectively have fields of view sufficiently broad to image a full width of the newly laid material.
  • a wide range of cameras can be used, including commercially available cameras capable of acquiring black-and-white images.
  • a camera 230 is a television or other type of video camera having an image sensor and a lens through which light passes when the camera is in operation.
  • Other types of cameras or image sensors can also be used, such as an infrared-sensitive camera, a visible light camera with infrared-pass filtration, a fiber-optic camera, a coaxial camera, charge-coupled device (CCD), or complementary metal oxide semiconductor (CMOS) sensor.
  • CCD charge-coupled device
  • CMOS complementary metal oxide semiconductor
  • the light and laser sources 218 and 224 are configured to illuminate the full width of the newly laid material 28 .
  • the illumination is reflected differently by inconsistencies in the material than by portions of the material that are free of inconsistencies. Such differences in illumination can be captured in images produced by the cameras 230 .
  • the frame 204 may be configured to shield the light sources and cameras so as to optimize the quality of imaging by the cameras 230 . It should be noted that various lighting and reflective configurations are possible. For example, a half-mirror could be used such that light from light sources is reflected by the mirror onto the material, and the cameras are directed not through, but past the mirror.
  • the light sources 216 include high-intensity red LEDs which produce area light. Other or additional types of lighting, including but not limited to fluorescent lights, could be used.
  • the quality and magnitude of surface illumination of the material 28 can be affected by ambient lighting and by reflectivity of the material. Accordingly, in one embodiment, one or more infrared light sources and/or light sources having an infrared component may be used to illuminate dark inconsistencies on a dark background.
  • a strobe or stroboscopic light source a noble gas arc lamp (e.g., xenon arc), metal arc lamp (e.g., metal halide) and/or laser (e.g., pulsed laser, solid state laser diode array and/or infrared diode laser array) could be used.
  • Power levels and wavelengths for light source(s) 216 may depend at least in part on the speed and sensitivity of the cameras 230 , speed at which the material 28 is being laid, delivery losses, and reflectivity of the material being inspected. For example, in another embodiment, wavelengths and power levels suitable for inspecting highly reflective materials may be employed.
  • Each laser source 224 and camera 230 can cover, e.g., material widths of between about three and four inches. Coverage could be greater or smaller than the foregoing range depending, for example, on lens type, distance between material and cameras and/or laser sources, and other factors. Depending, for example, on a width of material to be inspected and placement system configuration, different numbers of light sources, laser sources and/or cameras could be included to facilitate material inspection.
  • the system 200 thus can be scaled up or down to accommodate different material widths.
  • motion of the machine may be detected by the processor 40 , for example, via a code ring on the compaction roller and photo-interrupter as disclosed in U.S. patent application Ser. No. 10/726,099 entitled “Systems and Methods For Determining Inconsistency Characteristics of a Composite Structure”, the disclosure of which is incorporated herein in its entirety.
  • the processor 40 thereby determines that the machine 24 is in operation.
  • the processor 40 actuates the cameras 230 to obtain images at appropriate times based on movement of the machine 24 .
  • the processor 40 may actuate the cameras 230 to obtain images of material newly placed on the substrate 32 and which is currently being illuminated by the light and laser sources 216 and 224 .
  • the processor 40 may receive each image and may assign unique numbers to frames of the image data from the cameras 230 .
  • the processor 40 may store image frames in the memory 44 and may use them to track a linear position of the machine 24 as material is placed on the substrate 32 .
  • the processor 40 processes the image data in a frame to detect inconsistencies in the imaged section of material 28 .
  • the processor 40 also analyzes and displays selected inconsistencies on the user interface 50 .
  • An inconsistency dimension for example, an inconsistency width, can be determined as follows. After a digital image of an inconsistency has been acquired, a pixel set is selected from the digital image that represents the width of the inconsistency. The pixels in the pixel set are counted, and the count is correlated with distance to determine the inconsistency width.
  • the processor 40 may receive images from the cameras 230 and/or memory 44 and may process the images to facilitate the reliable detection of inconsistencies.
  • the processor 40 may display information on the user interface display screen 54 , for example, as shown in FIG. 8 .
  • a window 300 includes a frame 304 showing at least part of a section 308 of material 28 imaged by the cameras 230 . For example, an illuminated area 312 of the section 308 is shown in the window 300 .
  • Laser lines 320 produced by the laser sources 224 also are visible above the area 312 .
  • Inconsistencies 324 may be labeled and are shown in the window 300 .
  • a foreign object/debris (FOD) 330 struck by the laser lines 320 may be accentuated by the processor 40 for display in the frame 300 .
  • FOD foreign object/debris
  • the laser striping 320 can provide a “second-look” enhancement of areas lighted by the light sources 216 and thus can assist in revealing inconsistencies such as fuzz balls, resin balls, and backing materials. It should be noted, however, that although the laser striping 320 strikes the material 28 above the illuminated area 312 in the frame 300 , other arrangements of light source and laser source illumination are possible. In some embodiments, illumination from the light and laser sources 216 and 224 could be configured to overlap to a greater degree, or alternatively to strike material farther apart, than as shown in FIG. 8
  • images from the cameras 230 could be displayed in various ways on the user interface 50 .
  • images from two or more cameras 230 could be displayed simultaneously, e.g., side by side in a frame on the screen 54 , or sequentially in different frames.
  • the frame 300 may include a processed or unprocessed camera image. Additionally or alternatively, the frame may include an image that has been binarized. During binarization, all shades of gray above a predetermined threshold value can be changed to white, while all gray shades below the threshold are changed to black to heighten the contrast of inconsistencies and improve the accuracy of inconsistency detection. In other embodiments, the binarization operation need not be performed but instead the raw image, rates of change of the light levels in the raw image, and/or color changes in the images can be used to identify the inconsistencies.
  • implementations of the disclosure provide the ability to inspect wider bands of material more effectively than possible with current inspection systems, which use low-incident-angle side lighting to illuminate material under inspection.
  • the dual on-axis lighting provided by implementations of the disclosure can provide even illumination across material widths and is scalable to varying widths.

Abstract

A system and method of inspecting material laid by a material placement machine. Light is directed onto the material in a direction essentially normal to the material to illuminate a section of the material. Laser energy is projected onto the section at an angle predetermined to reveal inconsistencies in the section. This system provides improved illumination for material widths exceeding six inches and is scalable for inspecting various material widths.

Description

FIELD
The present disclosure relates generally to automated material placement machines and their use. More particularly (but not exclusively) the present disclosure relates to systems and methods for inspecting material laid by an automated material placement machine.
BACKGROUND
Automated material placement processes and machines are widely used in aerospace and other industries in the fabrication of large composite structures. Systems are available by which automated visual inspection can be performed while the material is being laid. These systems have been shown to be effective in reducing machine down-time for inspection purposes. Current inspection systems, however, have limited effectiveness when used to inspect materials wider than about six inches.
SUMMARY
The present disclosure, in one aspect, is directed to a method of inspecting material laid by a material placement machine. Light is directed onto the material in a direction essentially normal to the material to illuminate a section of the material. Laser energy is projected onto the section at an angle predetermined to reveal inconsistencies in the section.
In another aspect, the disclosure is directed to a system for inspecting material laid by a material placement machine. The system includes a mirror and one or more light sources configured to project light onto the mirror. The mirror is configured to reflect the projected light onto a section of the material in a direction essentially normal to the section. One or more laser sources are configured to project laser energy onto the section at an angle predetermined to reveal inconsistencies in the section.
In yet another aspect, the disclosure is directed to a system for inspecting material laid by a material placement machine. The system includes a mirror suspended over a section of the material that has been laid. The mirror has one or more transparent portions. One or more light sources are configured to project light onto one or more reflective portions of the mirror. The mirror is further configured to reflect the projected light onto the material section in a direction essentially normal to the section. One or more laser sources are configured to project laser energy onto the section at an angle predetermined to reveal inconsistencies in the section. One or more cameras are configured to record the section through the one or more transparent portions of the mirror.
Further areas of applicability of the present disclosure will become apparent from the detailed description provided hereinafter. It should be understood that the detailed description and specific examples, while indicating various preferred embodiments of the disclosure, are intended for purposes of illustration only and are not intended to limit the scope of the disclosure.
BRIEF DESCRIPTION OF THE DRAWINGS
The present disclosure will become more fully understood from the detailed description and the accompanying drawings, wherein:
FIG. 1 is a block diagram of a material placement system in accordance with one implementation of the disclosure;
FIG. 2 is a block diagram illustrating a method of inspecting material laid by a material placement system in accordance with one implementation of the disclosure;
FIG. 3 is a side perspective view of a system for inspecting material laid by a material placement system in accordance with one implementation of the disclosure;
FIG. 4 is a top/side perspective view of a system for inspecting material laid by a material placement system in accordance with one implementation of the disclosure;
FIG. 5 is a bottom/side perspective view of a system for inspecting material laid by a material placement system in accordance with one implementation of the disclosure;
FIG. 6 is a top view of a system for inspecting material laid by a material placement system in accordance with one implementation of the disclosure;
FIG. 7 is a bottom view of a system for inspecting material laid by a material placement system in accordance with one implementation of the disclosure; and
FIG. 8 is an illustration of a section of illuminated material and its image in a frame displayed on a user interface screen in accordance with one implementation of the disclosure.
DETAILED DESCRIPTION
The following description of various embodiments is merely exemplary in nature and is in no way intended to limit the disclosure, its application, or uses.
In some implementations, the disclosure is directed to systems and methods of inspecting material laid by a material placement machine. The placement machine could be, for example, a multi-head tape lamination machine (MHTLM), a fiber placement (FP) machine, or a contour tape lamination (CTL) machine. It should be noted that implementations of the disclosure may be practiced in connection with a wide variety of material placement machines and processes.
A block diagram of an exemplary material placement system is indicated generally in FIG. 1 by reference number 20. A material placement machine 24 is used to lay down composite material 28 onto a substrate 32 to fabricate a composite structure. The machine 24 includes a roller, compaction shoe and/or other component, numbered as 36 and dependent on the type of placement machine, for laying the material 28 onto the substrate 32. The system 20 includes a processor 40 having a memory and/or storage device 44. The processor 40 is in communication with the machine 24. A user interface 50 may be, e.g., a computer monitor including a display screen 54 and an input device such as a keyboard and mouse (not shown). The user interface 50 is in communication with the processor 40.
One implementation of a method of inspecting material laid by a material placement machine, e.g., the machine 24, is indicated generally in FIG. 2 by reference number 100. A width of the material 28 is newly laid on the substrate 32 by the machine 24. Light is directed onto the material 28 in a direction 120 essentially normal to the material to illuminate the material. Specifically and for example, the light is projected from a light source 124 onto a reflective surface 128 and reflected by the surface 128 onto the material 28 to illuminate a section 132 of the laid material. The method 100 also includes projecting laser energy onto the section 132 at an angle predetermined to reveal inconsistencies in the section 132. In the present implementation, a laser source 140 projects the laser energy as one or more lines 144 onto the section 132. The lines or stripes are projected, for example, across an axis 148 of placement of the material 28. It should be noted that other implementations are contemplated in which different laser patterns and/or laser projection orientations may be used.
The light source 124 above the material 28 may be configured to illuminate a full width of the material 28. The laser striping 144 can reveal gaps and/or overlaps in the material 28. Additionally, the striping can enhance the illumination from the light source 124 and can help reveal such items as fuzz balls, resin balls, and backing materials.
The present method can be implemented in various ways on various placement machines. Additionally, and as further described below, implementations of the present method can be scaled to various widths of material to be inspected. For example, although a single light source 124 and a single laser source 140 are used in the implementation 100, a plurality of light sources and/or a plurality of laser sources may be used in other implementations.
One exemplary embodiment of a system for inspecting material laid by a material placement machine is indicated generally in FIGS. 3-7 by reference number 200. The system 200 includes a frame 204 having brackets 208 configured for attachment to a placement machine, e.g., the machine 24 (shown in FIG. 1). It should be noted that other embodiments of the system 200 could be configured in various ways in relation to material placement machines, dependent on width of material to be inspected and placement machine configuration. For purposes of describing the present embodiment, it shall be assumed that component 36 of the machine 24 is a compaction roller. The frame 204 is configured for attachment, for example, above and behind the compaction roller 36 such that the frame 204 overhangs newly laid material 28. A mirror 212 is mounted in the frame 204, for example, at a 45-degree angle. The mirror 212 is at least partially silvered to provide one or more reflective portions.
A plurality of light sources 216 are mounted, for example, such that they project light essentially parallel to an axis 220 of placement of the material 28. Light from the light sources 216 may be projected toward the mirror 212 and reflected by the mirror reflective portion(s) onto the material 28 in a direction essentially normal to the material.
A plurality of laser sources 224 mounted to the frame 204 are configured to project laser energy directly onto the material 28 at an angle predetermined to reveal inconsistencies in the material. The laser sources 224 may be, for example, Lasaris™ SNF line lasers by StockerYale, Inc. of Salem, N.H.
A plurality of cameras 230 are mounted in the frame 204 above the mirror 212. The cameras 230 are configured to image, through one or more transparent portions 234 of the mirror 212, a section of the material 28 illuminated by the light and laser sources 216 and 224. The cameras 230 may be actuated, for example, by the processor 40, which receives images from the cameras 230 and/or memory 44. The processor 40 may process the images to facilitate reliable detection of inconsistencies.
The cameras 230 are, for example, Sony XC-HR50 cameras, although other cameras could be used. The cameras 230 collectively have fields of view sufficiently broad to image a full width of the newly laid material. A wide range of cameras can be used, including commercially available cameras capable of acquiring black-and-white images. In one embodiment, a camera 230 is a television or other type of video camera having an image sensor and a lens through which light passes when the camera is in operation. Other types of cameras or image sensors can also be used, such as an infrared-sensitive camera, a visible light camera with infrared-pass filtration, a fiber-optic camera, a coaxial camera, charge-coupled device (CCD), or complementary metal oxide semiconductor (CMOS) sensor.
The light and laser sources 218 and 224 are configured to illuminate the full width of the newly laid material 28. The illumination is reflected differently by inconsistencies in the material than by portions of the material that are free of inconsistencies. Such differences in illumination can be captured in images produced by the cameras 230. The frame 204 may be configured to shield the light sources and cameras so as to optimize the quality of imaging by the cameras 230. It should be noted that various lighting and reflective configurations are possible. For example, a half-mirror could be used such that light from light sources is reflected by the mirror onto the material, and the cameras are directed not through, but past the mirror.
In the present configuration, the light sources 216 include high-intensity red LEDs which produce area light. Other or additional types of lighting, including but not limited to fluorescent lights, could be used. The quality and magnitude of surface illumination of the material 28 can be affected by ambient lighting and by reflectivity of the material. Accordingly, in one embodiment, one or more infrared light sources and/or light sources having an infrared component may be used to illuminate dark inconsistencies on a dark background. In other embodiments, a strobe or stroboscopic light source, a noble gas arc lamp (e.g., xenon arc), metal arc lamp (e.g., metal halide) and/or laser (e.g., pulsed laser, solid state laser diode array and/or infrared diode laser array) could be used. Power levels and wavelengths for light source(s) 216 may depend at least in part on the speed and sensitivity of the cameras 230, speed at which the material 28 is being laid, delivery losses, and reflectivity of the material being inspected. For example, in another embodiment, wavelengths and power levels suitable for inspecting highly reflective materials may be employed.
In the configuration shown in FIGS. 3-7, two light sources 216, three laser sources 224, and three cameras 230 are used. Each laser source 224 and camera 230 can cover, e.g., material widths of between about three and four inches. Coverage could be greater or smaller than the foregoing range depending, for example, on lens type, distance between material and cameras and/or laser sources, and other factors. Depending, for example, on a width of material to be inspected and placement system configuration, different numbers of light sources, laser sources and/or cameras could be included to facilitate material inspection. The system 200 thus can be scaled up or down to accommodate different material widths.
When the machine 24 is in operation, motion of the machine may be detected by the processor 40, for example, via a code ring on the compaction roller and photo-interrupter as disclosed in U.S. patent application Ser. No. 10/726,099 entitled “Systems and Methods For Determining Inconsistency Characteristics of a Composite Structure”, the disclosure of which is incorporated herein in its entirety. The processor 40 thereby determines that the machine 24 is in operation. The processor 40 actuates the cameras 230 to obtain images at appropriate times based on movement of the machine 24. Specifically and for example, by tracking distances moved by the machine 24, the processor 40 may actuate the cameras 230 to obtain images of material newly placed on the substrate 32 and which is currently being illuminated by the light and laser sources 216 and 224. The processor 40 may receive each image and may assign unique numbers to frames of the image data from the cameras 230. The processor 40 may store image frames in the memory 44 and may use them to track a linear position of the machine 24 as material is placed on the substrate 32.
The processor 40 processes the image data in a frame to detect inconsistencies in the imaged section of material 28. The processor 40 also analyzes and displays selected inconsistencies on the user interface 50. An inconsistency dimension, for example, an inconsistency width, can be determined as follows. After a digital image of an inconsistency has been acquired, a pixel set is selected from the digital image that represents the width of the inconsistency. The pixels in the pixel set are counted, and the count is correlated with distance to determine the inconsistency width.
The processor 40 may receive images from the cameras 230 and/or memory 44 and may process the images to facilitate the reliable detection of inconsistencies. The processor 40 may display information on the user interface display screen 54, for example, as shown in FIG. 8. A window 300 includes a frame 304 showing at least part of a section 308 of material 28 imaged by the cameras 230. For example, an illuminated area 312 of the section 308 is shown in the window 300. Laser lines 320 produced by the laser sources 224 also are visible above the area 312. Inconsistencies 324 may be labeled and are shown in the window 300. A foreign object/debris (FOD) 330 struck by the laser lines 320 may be accentuated by the processor 40 for display in the frame 300. The laser striping 320 can provide a “second-look” enhancement of areas lighted by the light sources 216 and thus can assist in revealing inconsistencies such as fuzz balls, resin balls, and backing materials. It should be noted, however, that although the laser striping 320 strikes the material 28 above the illuminated area 312 in the frame 300, other arrangements of light source and laser source illumination are possible. In some embodiments, illumination from the light and laser sources 216 and 224 could be configured to overlap to a greater degree, or alternatively to strike material farther apart, than as shown in FIG. 8
It should be understood that in various implementations, images from the cameras 230 could be displayed in various ways on the user interface 50. For example, images from two or more cameras 230 could be displayed simultaneously, e.g., side by side in a frame on the screen 54, or sequentially in different frames.
The frame 300 may include a processed or unprocessed camera image. Additionally or alternatively, the frame may include an image that has been binarized. During binarization, all shades of gray above a predetermined threshold value can be changed to white, while all gray shades below the threshold are changed to black to heighten the contrast of inconsistencies and improve the accuracy of inconsistency detection. In other embodiments, the binarization operation need not be performed but instead the raw image, rates of change of the light levels in the raw image, and/or color changes in the images can be used to identify the inconsistencies.
The foregoing systems and methods provide improved illumination and inspection across varying material widths. Various implementations of the disclosure provide the ability to inspect wider bands of material more effectively than possible with current inspection systems, which use low-incident-angle side lighting to illuminate material under inspection. The dual on-axis lighting provided by implementations of the disclosure can provide even illumination across material widths and is scalable to varying widths.
While various preferred embodiments have been described, those skilled in the art will recognize modifications or variations which might be made without departing from the inventive concept. The examples illustrate the disclosure and are not intended to limit it. Therefore, the description and claims should be interpreted liberally with only such limitation as is necessary in view of the pertinent prior art.

Claims (19)

1. A method of inspecting material laid by a material placement machine comprising:
moving the placement machine to cause a frame attached above and behind a compaction device of the machine to overhang a section of the laid material;
directing light from one or more light sources mounted in the frame onto the laid section in a direction essentially normal to the laid section to illuminate the laid section;
projecting laser energy from one or more laser sources mounted to the frame onto the section at an angle predetermined to reveal inconsistencies in the section; and
using one or more cameras mounted above one or more transparent sections of a mirror mounted inside the frame to image the illuminated section through the one or more transparent sections.
2. The method of claim 1, wherein directing light comprises:
projecting the light toward a reflective surface mounted inside the frame; and
using the reflective surface to direct the projected light onto the material.
3. The method of claim 2, wherein the light is projected essentially parallel to an axis along which the placement machine moves.
4. The method of claim 1, wherein projecting laser energy comprises projecting one or more laser lines onto the section.
5. The method of claim 1, wherein projecting laser energy comprises extending at least a portion of each of the one or more laser sources below a lower edge of the frame.
6. The method of claim 1, further comprising selecting a number of the light sources and a number of the laser sources for performing the directing and projecting steps, the selecting performed based on a width of the section.
7. A system for inspecting material laid by a material placement machine, the system comprising:
a frame mounted to the placement machine and configured to extend over a section of material compacted by a compaction device of the placement machine;
a mirror mounted inside the frame at an angle configured to cause the mirror to reflect horizontally directed light onto the compacted section in a direction substantially normal to the compacted section;
one or more light sources mounted in the frame and configured to project light horizontally onto the mirror
one or more laser sources mounted to the frame and configured to project laser energy onto the compacted section at an angle predetermined to reveal inconsistencies in the section; and
one or more cameras mounted to the frame and configured to image the compacted section through the frame while the section is illuminated by the light and laser sources.
8. The system of claim 7, wherein the one or more cameras are configured to image the laid material based on movement of the placement machine.
9. The system of claim 8, wherein the mirror comprises one or more transparent portions through which the one or more cameras are configured to record the section.
10. The system of claim 8, wherein the one or more laser sources project one or more laser stripes onto the section.
11. The system of claim 7, wherein the one or more light sources are configured to project light essentially parallel to a surface over which the placement machine travels.
12. The system of claim 7, comprising a number of light sources and a number of laser sources configured based on a width of the section.
13. The system of claim 7, wherein the one or more light and one or more cameras are at least partially shielded by the frame.
14. A system for inspecting material laid by a material placement machine, the system comprising:
a mirror suspended over a section of the material that has been laid, the mirror having one or more transparent portions and mounted in a frame attached above and behind a compaction device of the machine;
one or more light sources mounted in the frame and configured to project light onto one or more reflective portions of the mirror, the mirror further configured to reflect the projected light onto the material section in a direction essentially normal to the section;
one or more laser sources mounted to the frame and configured to project laser energy onto the section at an angle predetermined to reveal inconsistencies in the section; and
one or more cameras mounted in the frame above the mirror and configured to record the section through the one or more transparent portions of the mirror.
15. The system of claim 14, wherein the one or more light sources are configured to project light along an axis of placement of the material.
16. The system of claim 14, wherein the one or more laser sources are configured to project light along an axis of placement of the material.
17. The system of claim 14, wherein the one or more laser sources are configured to project one or more laser lines onto the section.
18. The system of claim 14, wherein the one or more cameras are at least partly shielded by the frame.
19. The system of claim 14, scalable in accordance with a width of the section.
US11/264,076 2005-10-31 2005-10-31 Apparatus and methods for inspecting a composite structure for inconsistencies Active 2026-07-28 US7372556B2 (en)

Priority Applications (8)

Application Number Priority Date Filing Date Title
US11/264,076 US7372556B2 (en) 2005-10-31 2005-10-31 Apparatus and methods for inspecting a composite structure for inconsistencies
AU2006333500A AU2006333500B2 (en) 2005-10-31 2006-10-31 Apparatus and methods for inspecting a composite structure for defects
KR1020087002537A KR100996335B1 (en) 2005-10-31 2006-10-31 Apparatus and methods for inspecting a composite structure for inconsistencies
ES06849022T ES2734901T3 (en) 2005-10-31 2006-10-31 Apparatus and methods for inspecting a composite structure to detect defects
JP2008538119A JP5410092B2 (en) 2005-10-31 2006-10-31 Apparatus and method for inspecting composite structures for inconsistencies
CA2615117A CA2615117C (en) 2005-10-31 2006-10-31 Apparatus and methods for inspecting a composite structure for inconsistencies
PCT/US2006/042717 WO2007078408A2 (en) 2005-10-31 2006-10-31 Apparatus and methods for inspecting a composite structure for defects
EP06849022.6A EP1943502B1 (en) 2005-10-31 2006-10-31 Apparatus and methods for inspecting a composite structure for defects

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/264,076 US7372556B2 (en) 2005-10-31 2005-10-31 Apparatus and methods for inspecting a composite structure for inconsistencies

Publications (2)

Publication Number Publication Date
US20070097359A1 US20070097359A1 (en) 2007-05-03
US7372556B2 true US7372556B2 (en) 2008-05-13

Family

ID=37995824

Family Applications (1)

Application Number Title Priority Date Filing Date
US11/264,076 Active 2026-07-28 US7372556B2 (en) 2005-10-31 2005-10-31 Apparatus and methods for inspecting a composite structure for inconsistencies

Country Status (8)

Country Link
US (1) US7372556B2 (en)
EP (1) EP1943502B1 (en)
JP (1) JP5410092B2 (en)
KR (1) KR100996335B1 (en)
AU (1) AU2006333500B2 (en)
CA (1) CA2615117C (en)
ES (1) ES2734901T3 (en)
WO (1) WO2007078408A2 (en)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070034313A1 (en) * 2005-08-11 2007-02-15 The Boeing Company Systems and methods for in-process vision inspection for automated machines
US20100303335A1 (en) * 2003-12-02 2010-12-02 The Boeing Company Methods for Determining Inconsistency Characteristics of a Composite Structure
US20110017380A1 (en) * 2009-07-26 2011-01-27 The Boeing Company Mapping tow splices in composite structures
US20140081444A1 (en) * 2012-09-18 2014-03-20 Todd W. Rudberg Sequencer system for an automatic tape laying and projection system
US8934702B2 (en) 2003-12-02 2015-01-13 The Boeing Company System and method for determining cumulative tow gap width
US9618459B2 (en) 2015-05-18 2017-04-11 Flightware, Inc. Systems and methods for automated composite layup quality assurance
US9645095B2 (en) 2014-10-06 2017-05-09 The Boeing Company System and method for inspecting a composite part during manufacture
US10661512B2 (en) 2017-04-25 2020-05-26 The Boeing Company Measurement of ply boundaries
US10668673B2 (en) 2015-05-18 2020-06-02 Flightware, Inc. Systems and methods for automated composite layup quality assurance

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8068659B2 (en) * 2003-12-02 2011-11-29 The Boeing Company Method and system for determining cumulative foreign object characteristics during fabrication of a composite structure
US7978328B2 (en) * 2006-03-28 2011-07-12 The Boeing Company Vision inspection system device and method
US7362437B2 (en) * 2006-03-28 2008-04-22 The Boeing Company Vision inspection system device and method
US8050486B2 (en) * 2006-05-16 2011-11-01 The Boeing Company System and method for identifying a feature of a workpiece
US9052294B2 (en) * 2006-05-31 2015-06-09 The Boeing Company Method and system for two-dimensional and three-dimensional inspection of a workpiece
US20070277919A1 (en) * 2006-05-16 2007-12-06 The Boeing Company Systems and methods for monitoring automated composite manufacturing processes
DE102012104745B4 (en) * 2012-06-01 2015-03-19 SmartRay GmbH Test method and suitable test head
US8896827B2 (en) * 2012-06-26 2014-11-25 Kla-Tencor Corporation Diode laser based broad band light sources for wafer inspection tools
JP5988490B2 (en) 2012-12-25 2016-09-07 東レエンジニアリング株式会社 A device to inspect the application state of fiber reinforced plastic tape
US9606070B2 (en) 2014-11-25 2017-03-28 The Boeing Company Multispectral imaging system and method for detecting foreign object debris
US10794834B2 (en) 2015-06-08 2020-10-06 National Research Council Of Canada Real-time inspection of automated ribbon placement

Citations (76)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3879245A (en) 1972-06-27 1975-04-22 Composite Structures Corp Method of making composite cored structures
US4037941A (en) * 1975-06-30 1977-07-26 International Business Machines Corporation Inspection tool
US4064534A (en) 1976-04-20 1977-12-20 Leone International Sales Corporation System for monitoring the production of items which are initially difficult to physically inspect
US4310132A (en) 1978-02-16 1982-01-12 Nasa Fuselage structure using advanced technology fiber reinforced composites
US4548859A (en) 1984-10-12 1985-10-22 The Boeing Company Breather material and method of coating fabric with silicone rubber
US4601577A (en) * 1982-09-21 1986-07-22 Tokyo Shibaura Denki Kabushiki Kaisha Method and apparatus for detecting defects in a pattern
US4608220A (en) 1984-12-20 1986-08-26 The Boeing Company Method of forming composite material articles
US4693678A (en) 1986-01-15 1987-09-15 The Boeing Company Male layup-female molding system for fabricating reinforced composite structures
US4699683A (en) 1986-02-07 1987-10-13 The Boeing Company Multiroving fiber laminator
US4760444A (en) 1987-07-22 1988-07-26 Csd International, Inc. Machine visual inspection device and method
US4780262A (en) 1986-01-15 1988-10-25 The Boeing Company Method for making composite structures
US4790898A (en) 1982-07-19 1988-12-13 The Boeing Company Method and apparatus for fiber lamination
US4830298A (en) 1986-09-30 1989-05-16 The Boeing Company Self-centering sheave for filaments
EP0319797A2 (en) 1987-12-09 1989-06-14 Mitsui Mining & Smelting Co., Ltd. Method and apparatus for measuring defect density and defect distribution
US4877471A (en) 1984-08-24 1989-10-31 The Boeing Company Method and apparatus for delivering a resin-impregnated, multifilament band
US4941182A (en) 1987-07-29 1990-07-10 Phoenix Software Development Co. Vision system and method for automated painting equipment
US5024399A (en) 1988-06-08 1991-06-18 Societe Nationale Industrielle Et Aetospatiale Frame made of a composite material, especially for the fuselage of an aircraft, and its method of production
US5058497A (en) 1990-12-17 1991-10-22 Mcdonnell Douglas Corporation Compliant pressure roller
US5198983A (en) 1990-07-09 1993-03-30 Bell Helicopter Textron Inc. Method and apparatus for semi-automated insertion of conductors into harness connectors
US5278012A (en) * 1989-03-29 1994-01-11 Hitachi, Ltd. Method for producing thin film multilayer substrate, and method and apparatus for detecting circuit conductor pattern of the substrate
US5337647A (en) 1992-03-13 1994-08-16 The Boeing Company 3 dimensional braiding apparatus
WO1994018643A1 (en) 1993-02-02 1994-08-18 Golden Aluminum Company Method and apparatus for imaging surfaces
US5439549A (en) 1993-12-28 1995-08-08 The Boeing Company Double edged pressure sensitive folded tape application apparatus
US5450147A (en) 1992-09-28 1995-09-12 The Boeing Company Method for controlling projection of optical layup template utilizing cooperative targets
US5518208A (en) 1993-12-28 1996-05-21 The Boeing Company Optimum aircraft body frame to body skin shear tie installation pattern for body skin/stringer circumferential splices
US5540126A (en) 1994-05-26 1996-07-30 Piramoon Technologies Automatic lay-up machine for composite fiber tape
US5562788A (en) 1994-09-20 1996-10-08 The Boeing Company Composite material laser flaw detection
US5651600A (en) 1992-09-28 1997-07-29 The Boeing Company Method for controlling projection of optical layup template utilizing cooperative targets
US5684530A (en) * 1993-02-16 1997-11-04 Northeast Robotics, Inc. Continuous diffuse illumination method and apparatus
US5683646A (en) 1995-05-10 1997-11-04 Mcdonnell Douglas Corporation Fabrication of large hollow composite structure with precisely defined outer surface
US5700337A (en) 1996-03-01 1997-12-23 Mcdonnell Douglas Corporation Fabrication method for composite structure adapted for controlled structural deformation
EP0833146A2 (en) 1996-09-26 1998-04-01 The Boeing Company Method and apparatus for detecting and measuring laps and gaps in composite materials
US5746553A (en) 1996-04-08 1998-05-05 The Boeing Company Dual purpose lay-up tool
US5814386A (en) 1995-12-01 1998-09-29 Mcdonnell Douglas Corporation Composite shell formed as a body of rotation, and method and mandrel for making same
US5825495A (en) 1995-02-27 1998-10-20 Lockheed Martin Corporation Bright field illumination system
US5871117A (en) 1994-04-28 1999-02-16 Mcdonnell Douglas Corporation Tubular load-bearing composite structure
EP0903574A2 (en) 1997-08-18 1999-03-24 McDonnell Douglas Corporation Foreign object video detection and alert system and method
US5917588A (en) 1996-11-04 1999-06-29 Kla-Tencor Corporation Automated specimen inspection system for and method of distinguishing features or anomalies under either bright field or dark field illumination
US5979531A (en) 1997-10-01 1999-11-09 Mcdonnell Douglas Corporation Bi-directional fiber placement head
US6012883A (en) 1997-05-06 2000-01-11 The Boeing Company Hybrid lay-up tool
US6013341A (en) 1996-08-19 2000-01-11 Mcdonnell Douglas Corporation Carrying (bearing) pipe-casing made of composite materials, the method and the setting (straightening device) for its manufacturing
US6028673A (en) * 1998-03-31 2000-02-22 Ngk Spark Plug Co., Ltd. Inspection of solder bumps of bump-attached circuit board
US6045651A (en) 1993-09-07 2000-04-04 The Boeing Company Hand assisted lamination system
US6074716A (en) 1997-06-10 2000-06-13 Mcdonnell Douglas Corporation Weavable metal matrix impregnated tow composite material
US6086696A (en) 1998-07-21 2000-07-11 The Boeing Company Method of forming a seamless, cylindrical, thermoplastic structure with a multiple compaction roller winder
EP1030172A2 (en) 1999-02-18 2000-08-23 Parsytec Computer GmbH Method and device for detecting, marking and retrieving of defects in a material web
US6112792A (en) 1998-11-19 2000-09-05 The Boeing Company Fiber placement mid-span redirect
JP2001012930A (en) 1999-06-28 2001-01-19 Nissan Motor Co Ltd Surface defect inspection apparatus
US6205239B1 (en) 1996-05-31 2001-03-20 Texas Instruments Incorporated System and method for circuit repair
US6364250B1 (en) 1998-09-25 2002-04-02 Daimlerchrysler Aerospace Airbus Gmbh Shell component for an aircraft fuselage and method of manufacturing the same
US6369492B1 (en) 1998-04-15 2002-04-09 Matsushita Electronics Corporation Lighting unit with reflecting mirror
US6390169B1 (en) 2000-02-23 2002-05-21 The Boeing Company Conformable compaction apparatus for use with a fiber placement machine
US6451152B1 (en) 2000-05-24 2002-09-17 The Boeing Company Method for heating and controlling temperature of composite material during automated placement
US20020141632A1 (en) 2001-03-28 2002-10-03 The Boeing Company System and method for identifying defects in a composite structure
US6480271B1 (en) 2001-01-08 2002-11-12 The Boeing Company Traversing laser locating system
US6547769B2 (en) 1999-12-20 2003-04-15 Tricardia Llc Catheter apparatus with weeping tip and method of use
US6552783B1 (en) * 2000-06-28 2003-04-22 Teradyne, Inc. Optical system
US6633375B1 (en) * 1999-01-29 2003-10-14 Leica Microsystems Semiconductor Gmbh Method and device for optically examining structured surfaces of objects
US6639662B2 (en) 1997-09-19 2003-10-28 Kla-Tencor Corporation Sample inspection system
US6648273B2 (en) 2001-10-30 2003-11-18 The Boeing Company Light weight and high strength fuselage
US6692681B1 (en) 1997-01-29 2004-02-17 Raytheon Aircraft Company Method and apparatus for manufacturing composite structures
WO2004025385A1 (en) 2002-08-28 2004-03-25 Daimlerchrysler Method and device for operating an indicating unit on a working machine
US6721047B2 (en) * 2000-09-18 2004-04-13 Hitachi, Ltd. Method and apparatus for inspecting defects of a specimen
US20040098852A1 (en) 2002-11-22 2004-05-27 Nelson Paul E. Parallel configuration composite material fabricator
US6799619B2 (en) 2002-02-06 2004-10-05 The Boeing Company Composite material collation machine and associated method for high rate collation of composite materials
US20050023414A1 (en) 2003-07-28 2005-02-03 The Boeing Company Composite fuselage machine
US20050025350A1 (en) 2003-07-28 2005-02-03 Engelbart Roger W. Systems and method for identifying foreign objects and debris (FOD) and defects during fabrication of a composite structure
US20050039843A1 (en) 2003-08-22 2005-02-24 Johnson Brice A. Multiple head automated composite laminating machine for the fabrication of large barrel section components
US20050039842A1 (en) 2003-08-22 2005-02-24 The Boeing Company Unidirectional, multi-head fiber placement
US20050039844A1 (en) 2003-08-22 2005-02-24 The Boeing Company Automated composite lay-up to an internal fuselage mandrel
US6871684B2 (en) * 2002-08-13 2005-03-29 The Boeing Company System for identifying defects in a composite structure
US20050102814A1 (en) 2003-11-18 2005-05-19 The Boeing Company Method of transferring large uncured composite laminates
US20050117793A1 (en) 2003-12-02 2005-06-02 Engelbart Roger W. Systems and methods for determining defect characteristics of a composite structure
US20050203657A1 (en) 2004-03-12 2005-09-15 Engelbart Roger W. Systems and methods enabling automated return to and/or repair of defects with a material placement machine
US20050225753A1 (en) 2004-04-12 2005-10-13 Engelbart Roger W Systems and methods for using light to indicate defect locations on a composite structure
US20050263645A1 (en) 2004-04-06 2005-12-01 Kent Johnson Structural panels for use in aircraft fuselages and other structures

Family Cites Families (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS57132044A (en) * 1981-02-10 1982-08-16 Hitachi Metals Ltd Discriminating method of surface defect
JP2512093B2 (en) * 1988-07-29 1996-07-03 株式会社日立製作所 Foreign object detection device and method
JPH0267715A (en) * 1988-09-02 1990-03-07 Hitachi Ltd Aligner and its exposure
JPH0357241A (en) * 1989-07-26 1991-03-12 Hitachi Ltd Automatic external-appearance inspection apparatus
JPH04254707A (en) * 1991-01-30 1992-09-10 Nec Corp Appearance inspection device of plate body
JPH06109447A (en) * 1992-09-30 1994-04-19 Kawasaki Steel Corp Method and apparatus for measuring surface shape
JP3248635B2 (en) * 1993-01-22 2002-01-21 サンクス株式会社 Inspection equipment for translucent sheet-like objects
JPH07113620A (en) * 1993-10-14 1995-05-02 Aisin Seiki Co Ltd Appearance inspection system for soldered part
US20020054291A1 (en) * 1997-06-27 2002-05-09 Tsai Bin-Ming Benjamin Inspection system simultaneously utilizing monochromatic darkfield and broadband brightfield illumination sources
US6288780B1 (en) * 1995-06-06 2001-09-11 Kla-Tencor Technologies Corp. High throughput brightfield/darkfield wafer inspection system using advanced optical techniques
US5828495A (en) * 1997-07-31 1998-10-27 Eastman Kodak Company Lenticular image displays with extended depth
US6661912B1 (en) * 1998-08-03 2003-12-09 Hitachi Electronics Engineering Co., Ltd. Inspecting method and apparatus for repeated micro-miniature patterns
DE69703487T2 (en) * 1997-08-22 2001-06-13 Fraunhofer Ges Forschung Method and device for automatic inspection of moving surfaces
US6327374B1 (en) * 1999-02-18 2001-12-04 Thermo Radiometrie Oy Arrangement and method for inspection of surface quality
JP2000284552A (en) * 1999-03-31 2000-10-13 Minolta Co Ltd Image forming device
EP1089069A3 (en) * 1999-10-01 2001-08-29 CorkOpt Limited Linear illumination
JP2001118899A (en) * 1999-10-19 2001-04-27 Mitsubishi Electric Corp Inspection apparatus for foreign object and pattern defect
DE10122313A1 (en) * 2001-05-08 2002-11-21 Wolfgang P Weinhold Method and device for the contactless examination of an object, in particular with regard to its surface shape
JP4698140B2 (en) * 2003-11-12 2011-06-08 ザ・ボーイング・カンパニー System for identifying defects in composite structures
US9052294B2 (en) * 2006-05-31 2015-06-09 The Boeing Company Method and system for two-dimensional and three-dimensional inspection of a workpiece

Patent Citations (81)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3879245A (en) 1972-06-27 1975-04-22 Composite Structures Corp Method of making composite cored structures
US4037941A (en) * 1975-06-30 1977-07-26 International Business Machines Corporation Inspection tool
US4064534A (en) 1976-04-20 1977-12-20 Leone International Sales Corporation System for monitoring the production of items which are initially difficult to physically inspect
US4310132A (en) 1978-02-16 1982-01-12 Nasa Fuselage structure using advanced technology fiber reinforced composites
US4790898A (en) 1982-07-19 1988-12-13 The Boeing Company Method and apparatus for fiber lamination
US4601577A (en) * 1982-09-21 1986-07-22 Tokyo Shibaura Denki Kabushiki Kaisha Method and apparatus for detecting defects in a pattern
US4877471A (en) 1984-08-24 1989-10-31 The Boeing Company Method and apparatus for delivering a resin-impregnated, multifilament band
US4548859A (en) 1984-10-12 1985-10-22 The Boeing Company Breather material and method of coating fabric with silicone rubber
US4608220A (en) 1984-12-20 1986-08-26 The Boeing Company Method of forming composite material articles
US4693678A (en) 1986-01-15 1987-09-15 The Boeing Company Male layup-female molding system for fabricating reinforced composite structures
US4780262A (en) 1986-01-15 1988-10-25 The Boeing Company Method for making composite structures
US4699683A (en) 1986-02-07 1987-10-13 The Boeing Company Multiroving fiber laminator
US4830298A (en) 1986-09-30 1989-05-16 The Boeing Company Self-centering sheave for filaments
US4760444A (en) 1987-07-22 1988-07-26 Csd International, Inc. Machine visual inspection device and method
US4941182A (en) 1987-07-29 1990-07-10 Phoenix Software Development Co. Vision system and method for automated painting equipment
EP0319797A2 (en) 1987-12-09 1989-06-14 Mitsui Mining & Smelting Co., Ltd. Method and apparatus for measuring defect density and defect distribution
US5024399A (en) 1988-06-08 1991-06-18 Societe Nationale Industrielle Et Aetospatiale Frame made of a composite material, especially for the fuselage of an aircraft, and its method of production
US5278012A (en) * 1989-03-29 1994-01-11 Hitachi, Ltd. Method for producing thin film multilayer substrate, and method and apparatus for detecting circuit conductor pattern of the substrate
US5198983A (en) 1990-07-09 1993-03-30 Bell Helicopter Textron Inc. Method and apparatus for semi-automated insertion of conductors into harness connectors
US5058497A (en) 1990-12-17 1991-10-22 Mcdonnell Douglas Corporation Compliant pressure roller
US5337647A (en) 1992-03-13 1994-08-16 The Boeing Company 3 dimensional braiding apparatus
US5450147A (en) 1992-09-28 1995-09-12 The Boeing Company Method for controlling projection of optical layup template utilizing cooperative targets
US5651600A (en) 1992-09-28 1997-07-29 The Boeing Company Method for controlling projection of optical layup template utilizing cooperative targets
WO1994018643A1 (en) 1993-02-02 1994-08-18 Golden Aluminum Company Method and apparatus for imaging surfaces
US5684530A (en) * 1993-02-16 1997-11-04 Northeast Robotics, Inc. Continuous diffuse illumination method and apparatus
US6045651A (en) 1993-09-07 2000-04-04 The Boeing Company Hand assisted lamination system
US5439549A (en) 1993-12-28 1995-08-08 The Boeing Company Double edged pressure sensitive folded tape application apparatus
US5518208A (en) 1993-12-28 1996-05-21 The Boeing Company Optimum aircraft body frame to body skin shear tie installation pattern for body skin/stringer circumferential splices
US5871117A (en) 1994-04-28 1999-02-16 Mcdonnell Douglas Corporation Tubular load-bearing composite structure
US5540126A (en) 1994-05-26 1996-07-30 Piramoon Technologies Automatic lay-up machine for composite fiber tape
US5562788A (en) 1994-09-20 1996-10-08 The Boeing Company Composite material laser flaw detection
US5825495A (en) 1995-02-27 1998-10-20 Lockheed Martin Corporation Bright field illumination system
US5683646A (en) 1995-05-10 1997-11-04 Mcdonnell Douglas Corporation Fabrication of large hollow composite structure with precisely defined outer surface
US5814386A (en) 1995-12-01 1998-09-29 Mcdonnell Douglas Corporation Composite shell formed as a body of rotation, and method and mandrel for making same
US5700337A (en) 1996-03-01 1997-12-23 Mcdonnell Douglas Corporation Fabrication method for composite structure adapted for controlled structural deformation
US5804276A (en) 1996-03-01 1998-09-08 Mcdonnell Douglas Corporation Composite structure adapted for controlled structural deformation
US5746553A (en) 1996-04-08 1998-05-05 The Boeing Company Dual purpose lay-up tool
US6168358B1 (en) 1996-04-08 2001-01-02 The Boeing Company Hybrid lay-up tool
US6205239B1 (en) 1996-05-31 2001-03-20 Texas Instruments Incorporated System and method for circuit repair
US6013341A (en) 1996-08-19 2000-01-11 Mcdonnell Douglas Corporation Carrying (bearing) pipe-casing made of composite materials, the method and the setting (straightening device) for its manufacturing
EP0833146A2 (en) 1996-09-26 1998-04-01 The Boeing Company Method and apparatus for detecting and measuring laps and gaps in composite materials
US5963660A (en) 1996-09-26 1999-10-05 The Boeing Company Method and apparatus for detecting and measuring laps and gaps in composite materials
US5917588A (en) 1996-11-04 1999-06-29 Kla-Tencor Corporation Automated specimen inspection system for and method of distinguishing features or anomalies under either bright field or dark field illumination
US6692681B1 (en) 1997-01-29 2004-02-17 Raytheon Aircraft Company Method and apparatus for manufacturing composite structures
US6012883A (en) 1997-05-06 2000-01-11 The Boeing Company Hybrid lay-up tool
US6074716A (en) 1997-06-10 2000-06-13 Mcdonnell Douglas Corporation Weavable metal matrix impregnated tow composite material
EP0903574A2 (en) 1997-08-18 1999-03-24 McDonnell Douglas Corporation Foreign object video detection and alert system and method
US6639662B2 (en) 1997-09-19 2003-10-28 Kla-Tencor Corporation Sample inspection system
US5979531A (en) 1997-10-01 1999-11-09 Mcdonnell Douglas Corporation Bi-directional fiber placement head
US6028673A (en) * 1998-03-31 2000-02-22 Ngk Spark Plug Co., Ltd. Inspection of solder bumps of bump-attached circuit board
US6369492B1 (en) 1998-04-15 2002-04-09 Matsushita Electronics Corporation Lighting unit with reflecting mirror
US6086696A (en) 1998-07-21 2000-07-11 The Boeing Company Method of forming a seamless, cylindrical, thermoplastic structure with a multiple compaction roller winder
US6364250B1 (en) 1998-09-25 2002-04-02 Daimlerchrysler Aerospace Airbus Gmbh Shell component for an aircraft fuselage and method of manufacturing the same
US6112792A (en) 1998-11-19 2000-09-05 The Boeing Company Fiber placement mid-span redirect
US6633375B1 (en) * 1999-01-29 2003-10-14 Leica Microsystems Semiconductor Gmbh Method and device for optically examining structured surfaces of objects
US6725123B1 (en) 1999-02-18 2004-04-20 Parsytec Computer Gmbh Method and appliance for detecting, identifying and relocating defects in a material strip
EP1030172A2 (en) 1999-02-18 2000-08-23 Parsytec Computer GmbH Method and device for detecting, marking and retrieving of defects in a material web
JP2001012930A (en) 1999-06-28 2001-01-19 Nissan Motor Co Ltd Surface defect inspection apparatus
US6547769B2 (en) 1999-12-20 2003-04-15 Tricardia Llc Catheter apparatus with weeping tip and method of use
US6390169B1 (en) 2000-02-23 2002-05-21 The Boeing Company Conformable compaction apparatus for use with a fiber placement machine
US6451152B1 (en) 2000-05-24 2002-09-17 The Boeing Company Method for heating and controlling temperature of composite material during automated placement
US6552783B1 (en) * 2000-06-28 2003-04-22 Teradyne, Inc. Optical system
US6721047B2 (en) * 2000-09-18 2004-04-13 Hitachi, Ltd. Method and apparatus for inspecting defects of a specimen
US6480271B1 (en) 2001-01-08 2002-11-12 The Boeing Company Traversing laser locating system
US20020141632A1 (en) 2001-03-28 2002-10-03 The Boeing Company System and method for identifying defects in a composite structure
US6648273B2 (en) 2001-10-30 2003-11-18 The Boeing Company Light weight and high strength fuselage
US6799619B2 (en) 2002-02-06 2004-10-05 The Boeing Company Composite material collation machine and associated method for high rate collation of composite materials
US6814822B2 (en) 2002-02-06 2004-11-09 The Boeing Company Composite material collation machine and associated method for high rate collation of composite materials
US6871684B2 (en) * 2002-08-13 2005-03-29 The Boeing Company System for identifying defects in a composite structure
WO2004025385A1 (en) 2002-08-28 2004-03-25 Daimlerchrysler Method and device for operating an indicating unit on a working machine
US20040098852A1 (en) 2002-11-22 2004-05-27 Nelson Paul E. Parallel configuration composite material fabricator
US20050023414A1 (en) 2003-07-28 2005-02-03 The Boeing Company Composite fuselage machine
US20050025350A1 (en) 2003-07-28 2005-02-03 Engelbart Roger W. Systems and method for identifying foreign objects and debris (FOD) and defects during fabrication of a composite structure
US20050039843A1 (en) 2003-08-22 2005-02-24 Johnson Brice A. Multiple head automated composite laminating machine for the fabrication of large barrel section components
US20050039842A1 (en) 2003-08-22 2005-02-24 The Boeing Company Unidirectional, multi-head fiber placement
US20050039844A1 (en) 2003-08-22 2005-02-24 The Boeing Company Automated composite lay-up to an internal fuselage mandrel
US20050102814A1 (en) 2003-11-18 2005-05-19 The Boeing Company Method of transferring large uncured composite laminates
US20050117793A1 (en) 2003-12-02 2005-06-02 Engelbart Roger W. Systems and methods for determining defect characteristics of a composite structure
US20050203657A1 (en) 2004-03-12 2005-09-15 Engelbart Roger W. Systems and methods enabling automated return to and/or repair of defects with a material placement machine
US20050263645A1 (en) 2004-04-06 2005-12-01 Kent Johnson Structural panels for use in aircraft fuselages and other structures
US20050225753A1 (en) 2004-04-12 2005-10-13 Engelbart Roger W Systems and methods for using light to indicate defect locations on a composite structure

Non-Patent Citations (21)

* Cited by examiner, † Cited by third party
Title
A Barrelful of Experience, Intervia, May 1992, 2 pages.
Advanced Technology Tape Laying for Affordable Manufacturing of Large Composite Structures; http://www.cinmach.com/tech/pdf/TapeLayingGrimshaw.pdf; Michael N. Grimshaw, et al; 11 pages; 2001.
Automated Tape Laying; http://www.cinmach.com/tech/pdf/Grimshaw%20ASM%20Handbook.pdf; Michael N. Grimshaw; Cincinnati Machine; 6 pages; May 11, 2003.
BAe 146, Flight International, May 2, 1981, 2 pages.
Beechcraft's Composite Challenge, http://www.aerotalk.com/Beech.cfm, 2 pages; Apr. 13, 2003.
Business Aviation, Jun. 7, 2002, http://www.aviationnow.com/avnow/news/channel<SUB>-</SUB>busav.jsp?view=story&id=news/btoyo0607.xml, 1 page.
Expired U.S. Appl. No. 60/559,890, Biornstad et al., Apr. 6, 2004.
Expired U.S. Appl. No. 60/559,911, Johnson et al., Apr. 4, 2004.
Fiber Placement; http://www.cinmach.com/tech/pdf/asm<SUB>-</SUB>chapter<SUB>-</SUB>fp.pdf; Don O. Evans; Cincinnati Machine; 3 pages; Handbook of Composites published in 1998.
htpp://www.cinmach.com/compnews/PressReleases/pr00-11.htm; Raytheon Aircraft Orders Four More Fiber Cincinnati Fiber Placement Systems for Industry's First Composite-Fuselage Business Jets, 1 page; Jul. 20, 2000.
htpp://www.rockymountaincomposites.com/wind-sys.htm: Filament Winding, 1 page; 2000.
http://www.cinmach.com/WolfTracks4-1/MTG-WT7.htm; Premier I Features Lighter, Stronger, All-Composite Fuselage, 1 page; 1998.
Krupka, R; Walz, T; Ettemeyer, A: "Industrial Applications of Shearography for Inspection of Aircraft Components" Proceedings of the 8th European Conference of Nondestructive Testing< Barcelona (Spain), Jun. 17-21, 2002, 'Online! Jun. 30, 2002, XP002351899 NDT.NET-Feb. 2003, vol. 8, No. 2 Retrieved from the Internet: URL:http://www.ndt.net/articl/ecndt02/484/484.htm> 'retrieved on Oct. 31, 2005!.
Office Action Summary from the USPTO mailed Oct. 18, 2006 in reference to U.S. Appl. No. 10/846,974, filed May 14, 2004, first named inventor Roger W. Engelbart.
Pending U.S. Appl. No. (not yet assigned) entitled Composite Barrel Sections for Aircraft Fuselages and Other Structures, and Methods and Systems for Manufacturing Such Barrel Sections, Biornstad et al., filed May 20, 2004.
Pending U.S. Appl. No. 10/819,084, Turnmire et al., filed Apr. 6, 2004.
Pending utility U.S. Appl. No. 10/949,848, Stulc, Sep. 23, 2004.
Raytheon Aircraft's Hawker Horizon Reaches Fuselage Milestone, Raytheon News Release; http://www.beechcraft.de/Presse/2000/100900b.htm; 2 pages; Oct. 9, 2000.
Raytheon, Mar. 2000, vol. 4, No. 2, http://www.cts.com/king/vasci/newsletter/vol42.html, 2 pages.
Sharp et al., "Material Selection/Fabrication Issues for Thermoplastic Fiber Placement", Journal of Thermosplastic Composite Materials, vol. 8; Jan. 1995, p. 2-14.
U.S. Appl. No. 10/628,691 entitled Systems and Methods for Identifying Foreign Objects and Debris (FOD) and Defects During Fabrication of a Composite Structure, Engelbart et al., filed Jul. 28, 2003.

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8934702B2 (en) 2003-12-02 2015-01-13 The Boeing Company System and method for determining cumulative tow gap width
US8184281B2 (en) 2003-12-02 2012-05-22 The Boeing Company Methods for determining inconsistency characteristics of a composite structure
US20100303335A1 (en) * 2003-12-02 2010-12-02 The Boeing Company Methods for Determining Inconsistency Characteristics of a Composite Structure
US9027621B2 (en) * 2005-08-11 2015-05-12 The Boeing Company Vision inspection during application of composite tape
US8668793B2 (en) * 2005-08-11 2014-03-11 The Boeing Company Systems and methods for in-process vision inspection for automated machines
US20070034313A1 (en) * 2005-08-11 2007-02-15 The Boeing Company Systems and methods for in-process vision inspection for automated machines
US20140124142A1 (en) * 2005-08-11 2014-05-08 The Boeing Company Vision inspection during application of composite tape
US20110017380A1 (en) * 2009-07-26 2011-01-27 The Boeing Company Mapping tow splices in composite structures
US8753458B2 (en) 2009-07-26 2014-06-17 The Boeing Company Mapping tow splices in composite structures
US8695669B2 (en) 2009-07-26 2014-04-15 The Boeing Company Mapping tow splices in composite structures
US20140081444A1 (en) * 2012-09-18 2014-03-20 Todd W. Rudberg Sequencer system for an automatic tape laying and projection system
US9645095B2 (en) 2014-10-06 2017-05-09 The Boeing Company System and method for inspecting a composite part during manufacture
US9618459B2 (en) 2015-05-18 2017-04-11 Flightware, Inc. Systems and methods for automated composite layup quality assurance
US10668673B2 (en) 2015-05-18 2020-06-02 Flightware, Inc. Systems and methods for automated composite layup quality assurance
US10661512B2 (en) 2017-04-25 2020-05-26 The Boeing Company Measurement of ply boundaries

Also Published As

Publication number Publication date
US20070097359A1 (en) 2007-05-03
JP5410092B2 (en) 2014-02-05
KR20080031922A (en) 2008-04-11
JP2009513984A (en) 2009-04-02
KR100996335B1 (en) 2010-11-23
EP1943502A2 (en) 2008-07-16
ES2734901T3 (en) 2019-12-12
WO2007078408A3 (en) 2007-10-04
EP1943502B1 (en) 2019-04-10
CA2615117A1 (en) 2007-07-12
CA2615117C (en) 2015-04-28
AU2006333500A1 (en) 2007-07-12
AU2006333500B2 (en) 2010-10-21
WO2007078408A2 (en) 2007-07-12

Similar Documents

Publication Publication Date Title
US7372556B2 (en) Apparatus and methods for inspecting a composite structure for inconsistencies
CN110596134B (en) Sheet glass edge flaw detection method based on image acquisition
US7889907B2 (en) Apparatus and methods for inspecting tape lamination
US8179434B2 (en) System and method for imaging of curved surfaces
KR101679205B1 (en) Device for detecting defect of device
US7869021B2 (en) Multiple surface inspection system and method
JP5589423B2 (en) Transparent flat plate detection system
JP2008170256A (en) Flaw detection method, flaw detection program and inspection device
JPH11271038A (en) Painting defect inspection device
CN110402386A (en) Cylinder surface examining device and cylinder surface inspecting method
JP4398282B2 (en) Pantograph slip board inspection device.
KR20160149883A (en) An apparatus for inspecting a lens defect
JP2010151484A (en) Device and method for inspecting substrate

Legal Events

Date Code Title Description
AS Assignment

Owner name: BOEING COMPANY, THE, ILLINOIS

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:ENGELBART, ROGER W.;HANNEBAUM, REED;POLLOCK, TIM;AND OTHERS;REEL/FRAME:018131/0411;SIGNING DATES FROM 20051014 TO 20051031

STCF Information on status: patent grant

Free format text: PATENTED CASE

FPAY Fee payment

Year of fee payment: 4

FPAY Fee payment

Year of fee payment: 8

MAFP Maintenance fee payment

Free format text: PAYMENT OF MAINTENANCE FEE, 12TH YEAR, LARGE ENTITY (ORIGINAL EVENT CODE: M1553); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY

Year of fee payment: 12